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公开(公告)号：KR1020100078911A
公开(公告)日：2010-07-08
申请号：KR1020080137294
申请日：2008-12-30
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A drive unit of the multiple solar arrays for a satellite is provided to install a plurality of solar arrays on both sides of a satellite by changing the structure of a driving unit with a high-temperature fluid blocking valve. CONSTITUTION: A high-temperature fluid blocking valve comprises a support shaft(200), a support member(300), and a rotating motor(500). The support shaft is installed on both sides of the satellite to be able to be disappeared by a driving unit. The support member is installed on the outer end of the support shaft. The support member includes one or more installation surfaces. The rotating motor is installed on the installation surfaces of the support member. The rotating motor is connected to a solar array. The rotating motor rotates the solar array.
Abstract translation: 目的：提供用于卫星的多个太阳能阵列的驱动单元，以通过用高温流体阻断阀改变驱动单元的结构来在卫星的两侧上安装多个太阳能阵列。 构成：高温流体阻塞阀包括支撑轴（200），支撑构件（300）和旋转马达（500）。 支撑轴安装在卫星的两侧，以便能够被驱动单元消失。 支撑构件安装在支撑轴的外端上。 支撑构件包括一个或多个安装表面。 旋转马达安装在支撑件的安装表面上。 旋转马达连接到太阳能阵列。 旋转电机旋转太阳能电池阵列。
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公开(公告)号：KR1020010058821A
公开(公告)日：2001-07-06
申请号：KR1019990066190
申请日：1999-12-30
IPC: B64G1/00
Abstract: PURPOSE: A triaxial position controlling structure for a satellite is provided to reduce load by removing unnecessary area of the structure and to easily insert the structure by attaching a guide structure. CONSTITUTION: A triaxial position controlling structure comprises a satellite simulation structure(1) installing components on a vertical plate(2) and a horizontal plate(3); a screw groove(4) installed on the horizontal plate with a specific interval to conveniently arrange the component; a space(6) formed on the horizontal plate and the vertical plate to reduce load; a guide structure(5) vertically attached on the vertical plate to easily insert the horizontal plate; and a middle horizontal plate(3) fixed on an air bearing(7) to lower specific gravity of the satellite simulation structure. The load of the air bearing is reduced by removing the unnecessary space of the horizontal and vertical plates of the satellite simulation structure. Moreover, the space and the screw groove arrange assembled components without releasing the satellite simulation structure.
Abstract translation: 目的：提供一种用于卫星的三轴位置控制结构，通过去除结构的不必要区域，并通过安装引导结构容易地插入结构来减轻负载。 构成：三轴位置控制结构包括在垂直板（2）和水平板（3）上安装部件的卫星模拟结构（1）。 以特定间隔安装在水平板上的螺丝槽（4），以方便地布置部件; 形成在水平板和垂直板上的空间（6），以减轻负载; 垂直安装在垂直板上的引导结构（5），以便容易地插入水平板; 和固定在空气轴承（7）上的中间水平板（3），以降低卫星模拟结构的比重。 通过去除卫星模拟结构的水平和垂直板的不必要的空间来减小空气轴承的负载。 此外，空间和螺纹槽布置组装的部件，而不会释放卫星模拟结构。
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公开(公告)号：KR100942010B1
公开(公告)日：2010-02-12
申请号：KR1020070140751
申请日：2007-12-28
Applicant: 한국항공우주연구원
IPC: B64G1/22
Abstract: 본 발명은 위성용 우주분진물 분사장치에 관한 것으로서, 우주분진물을 수거하는 위성에 탑재된 분사장치에 있어서, 상기 분사장치는, 개구된 일단부로 우주분진물이 분사되는 본체와; 상기 본체에 삽입되어 내장되고 그 일단부는 수거된 우주분진물과 접하는 분사면으로 형성된 스프링과; 상기 본체에 설치되고 모터에 의해 회전 구동되는 스크류축과; 상기 스크류축에 의해 본체의 축방향을 따라 이동되면서 스프링을 압축 및 인장시키는 고정핀;을 포함하여 구성된 것을 특징으로 하여, 경제적이고 효율적이다.
위성, 우주, 분진물, 잔해, 분사, 대기권, 스프링, 분사면-
公开(公告)号：KR1020090072594A
公开(公告)日：2009-07-02
申请号：KR1020070140751
申请日：2007-12-28
Applicant: 한국항공우주연구원
IPC: B64G1/22
Abstract: A cosmic dust injection system for a satellite is provided to heighten profitability because the expendable fuel like propellant is not used. A cosmic dust injection system for a satellite comprises a main body(110) in which cosmic dust is emitted to one opened end, a spring(150) which is inserted into the main body, whereof one end is formed with the jetting surface contacting with the cosmic dust, a screw shaft(120) which is installed in the main body and rotates with the motor, and a fixation pin(130) which compresses and releases the spring.
Abstract translation: 提供用于卫星的宇宙除尘注入系统，以提高利润率，因为不使用消耗性燃料如推进剂。 用于卫星的宇宙粉尘喷射系统包括：主体（110），其中将宇宙尘埃发射到一个开放端;弹簧（150），其插入主体中，其一端形成有与 宇宙尘埃，安装在主体中并与电动机一起旋转的螺杆轴（120）和压缩并释放弹簧的固定销（130）。
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15.发明公开
公开(公告)号：KR1020080003296A
公开(公告)日：2008-01-07
申请号：KR1020070133556
申请日：2007-12-18
Applicant: 한국항공우주연구원
IPC: G01S5/14
Abstract: A method and an apparatus for determining GEO stationary satellite attitude and orbit using multiple ground based GPS signal transceivers are provided to determine the attitude and the position of a GEO stationary satellite using the GPS signal transmitted from the multiple ground based GPS transceivers. According to an apparatus for determining GEO stationary satellite attitude and orbit, a number of ground base stations transmit a GPS signal by being installed on the ground. A number of antennas receive the GPS signal by being installed on a stationary satellite. A calculation part calculates the attitude and orbit of the GEO stationary satellite by analyzing the GPS signal received by the antennas.
Abstract translation: 提供了一种用于使用多个基于地面的GPS信号收发器来确定GEO固定卫星姿态和轨道的方法和装置，以使用从多个基于地面的GPS收发器发送的GPS信号来确定GEO固定卫星的姿态和位置。 根据用于确定GEO固定卫星姿态和轨道的装置，许多地面基站通过安装在地面上传输GPS信号。 许多天线通过安装在固定卫星上来接收GPS信号。 计算部分通过分析由天线接收的GPS信号来计算GEO固定卫星的姿态和轨道。
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Patent Agency Ranking
公开(公告)号：KR100417950B1
公开(公告)日：2004-02-11
申请号：KR1019990066193
申请日：1999-12-30
IPC: B64G1/00
Abstract: PURPOSE: A triaxial position control testing device of a satellite is provided to inspect a triaxial position control system on a ground. CONSTITUTION: A triaxial position control testing device comprises a satellite simulation structure(1) of a hexahedron mounting structure; an air bearing(2) flying the satellite simulation structure by compression air(7); nozzles(4,5,6) generating position control thrust of the satellite simulation structure by being applied the compression air; and a mounted computer controlling driving of the nozzle according to a position control sensor input. The air bearing is fixed on a middle plate(3) to lower specific gravity by installing the mounted component of the satellite in the satellite simulation structure. Thrust of the satellite simulation structure injects thrust by the compression air.
Abstract translation: 目的：提供卫星的三轴位置控制测试装置，以检查地面上的三轴位置控制系统。 构成：三轴位置控制测试装置包括六面体安装结构的卫星模拟结构（1） 空气轴承（2）通过压缩空气（7）飞行卫星模拟结构; 通过施加压缩空气产生卫星模拟结构的位置控制推力的喷嘴（4,5,6） 以及安装的计算机，根据位置控制传感器输入控制喷嘴的驱动。 通过将卫星的安装部件安装在卫星模拟结构中，空气轴承固定在中间板（3）上以降低比重。 卫星模拟结构的推力由压缩空气注入推力。
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公开(公告)号：KR1019990051765A
公开(公告)日：1999-07-05
申请号：KR1019970071143
申请日：1997-12-12
IPC: B64G7/00
Abstract: 본 발명은 고가의 첨단시스템의 인공위성의 발사전에 지상에서 피치방향에 대한 충분한 실험을 할 수 있도록 하는 인공위성 자세제어 모의실험을 위한 1축 회전 시뮬레이터에 관한 것이다.
이러한 본 발명은 고정 수평받침대와, 상기 고정 수평받침대 상부에 회전가능하게 결합된 회전수평받침대와, 회전 수평받침대 상부중앙에 설치되고 회전 수평받침대의 위치 변화값을 검출하는 포텐셔 미터와, 상기 포텐셔 미터를 결합 고정시키는 결합수단과, 회전 수평받침대 상부에 설치되고 회전 수평받침대의 회전 토오크를 발생시키는 출력수단과, 회전 수평받침대의 각속도를 검출하는 각속도센서와, 상기 검출 데이타를 획득하고 연산처리하는 데이타 획득 연산수단을 구비시킴으로써 이루어진다.-
公开(公告)号：KR101264853B1
公开(公告)日：2013-05-15
申请号：KR1020120157449
申请日：2012-12-28
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A walking assist device in space is provided to allow walk similar to gravity walk because attractive force is formed by magnetic bodies attached to the shoes of the astronauts and an electromagnet field. CONSTITUTION: A walking assist device in space comprises magnetic bodies(10), an electromagnet field(20), and a controller(30). The magnetic bodies are arranged on the bottom of shoes. The electromagnet field comprises multiple electromagnets embedded along walking paths and work positions; and a walking surface installed above the electromagnets. The controller is connected to the electromagnets and selectively applies power to the electromagnets. The controller alternately form the N-poles and S-poles of the electromagnets installed along the walking paths and work positions. [Reference numerals] (10) Magnetic body; (11) Spacesuit; (12) Electronic tag; (20) Electromagnet field; (30) Controller; (40) Electronic tag reader
Abstract translation: 目的：提供空间中的行走辅助装置，以使行走类似于重力行走，因为吸引力是由附着在宇航员和电磁场的鞋身上的磁性体形成的。 构成：空间中的行走辅助装置包括磁体（10），电磁场（20）和控制器（30）。 磁体布置在鞋底上。 电磁场包括沿着步行路径和工作位置嵌入的多个电磁体; 以及安装在电磁铁上方的行走表面。 控制器连接到电磁铁，并有选择地向电磁铁供电。 控制器交替地形成沿着步行路径和工作位置安装的电磁体的N极和S极。 （附图标记）（10）磁性体; （11）太空服 （12）电子标签; （20）电磁场; （30）控制器; （40）电子标签阅读器
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公开(公告)号：KR101059437B1
公开(公告)日：2011-08-25
申请号：KR1020080137305
申请日：2008-12-30
Applicant: 한국항공우주연구원
Abstract: 본 발명은 인공위성의 양 측면에 구동부에 의해 출몰 가능하도록 설치되는 지지축과, 상기 지지축의 외단부에 설치되며 적어도 하나 이상의 설치면을 갖는 지지부재와, 상기 지지부재의 설치면에 설치되되, 태양전지판에 연결되어 태양전지판을 회전시키는 회전모터로 구성되는 것을 특징으로 한다.
본 발명에 의하면, 인공위성 태양전지판 구동장치의 구조를 변경함으로써 인공위성의 양 측면에 다수의 태양전지판을 각각 회전 가능하게 설치할 수 있어 인공위성을 3축 방향으로 자세 제어할 수 있는 효과가 있다.
인공위성, 태양전지판, 태양복사압, 모멘텀 덤핑, 추력기, 자세제어Abstract translation: 本发明doedoe安装在安装支撑构件的安装表面上，具有安装表面的支撑轴中的至少一个与支承轴，其被安装成可通过驱动单元侵染对卫星的任一侧的外端部的支撑部件，太阳 连接到太阳能电池板以旋转太阳能电池板的旋转电机。
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公开(公告)号：KR100467507B1
公开(公告)日：2005-01-24
申请号：KR1020020058621
申请日：2002-09-27
Applicant: 한국항공우주연구원
Inventor： 박영웅
IPC: B64G1/10
Abstract: PURPOSE: Pyramid-type reaction wheel momentum management algorithm of a geostationary orbit artificial satellite is provided to automatically manage the reaction wheel algorithm by separately discriminating the momentum management algorithm at a dumping mode and a station keeping mode. CONSTITUTION: Pyramid-type reaction wheel momentum(W1,W2,W3,W4) management algorithm of a geostationary orbit artificial satellite automatically manages steps of deciding dumping execution by separating a stable region and a normal operation range for the current reaction wheel momentum, separately considering a thruster set for four reaction wheels, and then deciding a thruster set adequate to produce torque in 3-axis directions. At a station keeping mode, the pyramid-type reaction wheel momentum management algorithm of the geostationary orbit artificial satellite calculates a torque value to be controlled for disturbance, decides the dumping state when the reaction wheel momentum is not in the stable region, and executes attitude control, using reaction wheels when the torque direction to be controlled and the torque direction to be dumped are not coincided.
Abstract translation: 目的：提供一种对地静止轨道人造卫星的金字塔型反应轮动量管理算法，通过在倾卸模式和站点保持模式下分别区分动量管理算法来自动管理反应轮算法。 组成：对地静止轨道人造卫星的金字塔型反应轮动量（W1，W2，W3，W4）管理算法通过分离当前反应轮动量的稳定区域和正常操作范围，自动管理决定倾倒执行的步骤 考虑用于四个反作用轮的推力器组，然后确定适合于在三轴方向上产生扭矩的推力器组。 在站台保持模式下，对地静止轨道人造卫星的金字塔型反应轮动量管理算法计算待扰动的扭矩值，确定反应轮动量不在稳定区域时的倾卸状态，并执行姿态 当要控制的转矩方向与要转储的转矩方向不一致时，使用反作用轮来控制。
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